Airfoil shape for a compressor

ABSTRACT

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

RELATED APPLICATIONS

The present application is related to [GE DOCKET NUMBERS 247346, 247350, 259403 and 259560] filed concurrently herewith, which are each fully incorporated by reference herein and made a part hereof.

BACKGROUND OF THE INVENTION

The present invention relates generally to an airfoil for use in turbomachinery, and more particularly relates to an airfoil profile or airfoil shape for use in a compressor.

In turbomachines, many system requirements should be met at each stage of the turbomachine's flow path to meet design goals. These design goals include, but are not limited to, overall improved efficiency, reduction of vibratory response and improved airfoil loading capability. For example, a compressor airfoil profile should achieve thermal and mechanical operating requirements for a particular stage in the compressor. Moreover, component lifetime, reliability and cost targets also should be met.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect of the present invention an article of manufacture is provided having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

According to another aspect of the present invention an article of manufacture is provided having a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, the X, Y and Z coordinate values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up and scaled-down airfoil profile.

According to yet another aspect of the present invention a compressor is provided having a plurality of inlet guide vanes, each of the inlet guide vanes including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape.

These and other features and improvements of the present invention should become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic representation of a compressor flow path through multiple stages and illustrates exemplary compressor stages according to an aspect of the invention;

FIG. 2 is a perspective view of an inlet guide vane, according to an aspect of the invention; and

FIG. 3 is a cross-sectional view of the inlet guide vane airfoil taken generally about on line 3-3 in FIG. 2, according to an aspect of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

One or more specific aspects/embodiments of the present invention will be described below. In an effort to provide a concise description of these aspects/embodiments, all features of an actual implementation may not be described in the specification. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with machine-related, system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.

When introducing elements of various embodiments of the present invention, the articles “a,” “an,” “the,” and “said” are intended to mean that there are one or more of the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements. Any examples of operating parameters and/or environmental conditions are not exclusive of other parameters/conditions of the disclosed embodiments. Additionally, it should be understood that references to “one embodiment”, “one aspect” or “an embodiment” or “an aspect” of the present invention are not intended to be interpreted as excluding the existence of additional embodiments or aspects that also incorporate the recited features. Turbomachinery is defined as one or more machines that transfer energy between a rotor and a fluid or vice-versa, including but not limited to gas turbines, steam turbines and compressors.

Referring now to the drawings, FIG. 1 illustrates an axial compressor flow path 1 of a compressor 2 that includes a plurality of compressor stages. The compressor 2 may be used in conjunction with, or as part of, a gas turbine. As one non-limiting example only, the compressor flow path 1 may comprise about eighteen rotor/stator stages. However, the exact number of rotor and stator stages is a choice of engineering design, and may be more or less than the illustrated eighteen stages. It is to be understood that any number of rotor and stator stages can be provided in the compressor, as embodied by the invention. The eighteen stages are merely exemplary of one turbine/compressor design, and are not intended to limit the invention in any manner.

The compressor rotor blades 22 impart kinetic energy to the airflow and therefore bring about a desired pressure rise. Directly following the rotor blades 22 is a stage of stator compressor vanes 23. However, in some designs the stator vanes may precede the rotor blades. Both the rotor blades and stator vanes turn the airflow, slow the airflow velocity (in the respective airfoil frame of reference), and yield a rise in the static pressure of the airflow. Typically, multiple rows of rotor/stator stages are arranged in axial flow compressors to achieve a desired discharge to inlet pressure ratio. Each rotor blade and stator vane includes an airfoil, and these airfoils can be secured to rotor wheels or a stator case by an appropriate attachment configuration, often known as a “root,” “base” or “dovetail” (not shown). In addition, compressors may also include inlet guide vanes (IGVs) 21, variable stator vanes (VSVs) 25 and exit or exhaust guide vanes (EGVs) 27. In some applications, the VSVs 25 may be located towards the front (or inlet) of the compressor. All of these blades and vanes have airfoils that act on the medium (e.g., air) passing through the compressor flow path 1.

Exemplary stages of the compressor 2 are illustrated in FIG. 1. One stage of the compressor 2 comprises a plurality of circumferentially spaced rotor blades 22 mounted on a rotor wheel 51 and a plurality of circumferentially spaced stator vanes 23 attached to a static compressor case 59. Each of the rotor wheels 51 may be attached to an aft drive shaft 58, which may be connected to the turbine section of the engine. The rotor blades 22 and stator vanes 23 lie in the flow path 1 of the compressor 2. The direction of airflow through the compressor flow path 1, as embodied by the invention, is indicated by the arrow 60 (FIG. 1), and flows generally from left to right in the illustration. The rotor blades and stator vanes herein of the compressor 2 are merely exemplary of the stages of the compressor 2 within the scope of the invention. In addition, each inlet guide vane 21, rotor blade 22, stator vane 23, variable stator vane 25 and exit guide vane 27 may be considered an article of manufacture. Further, the article of manufacture may comprise an inlet guide vane configured for use with a compressor.

An inlet guide vane 21, illustrated in FIG. 2, is provided with an airfoil 200. Each of the inlet guide vanes 21 has an airfoil profile at any cross-section from the airfoil root 220 to the airfoil tip 210. Referring to FIG. 3, it will be appreciated that each inlet guide vane 21 has an airfoil 200 as illustrated. The airfoil 200 has a suction side 310 and a pressure side 320. The suction side 310 is located on the opposing side of the airfoil from the pressure side 320. Thus, each of the inlet guide vanes 21 has an airfoil profile at any cross-section in the shape of the airfoil 200. The airfoil 200 also includes a leading edge 330 and a trailing edge 340, and a chord length 350 extends therebetween. The root of the airfoil corresponds to the lowest non-dimensional Z value of scalable Table 1. The tip of the airfoil corresponds to the highest non-dimensional Z value of scalable Table 1. An airfoil may extend beyond the compressor flowpath and may be tipped to achieve the desired endwall clearances. As one example only, the height of the airfoil 200 may be from about 1 inch to about 50 inches or more, about 5 inches to about 40 inches, or about 10 inches to about 30 inches. However, any specific airfoil height may be used as desired in the specific application.

The compressor flow path 1 requires airfoils that meet system requirements of aerodynamic and mechanical blade/vane loading and efficiency. For example, it is desirable that the airfoils are designed to reduce the vibratory response or vibratory stress response of the respective blades and/or vanes. Materials such as high strength alloys, non-corrosive alloys and/or stainless steels may be used in the blades and/or vanes. To define the airfoil shape of each blade airfoil and/or vane airfoil, there is a unique set or loci of points in space that meet the stage requirements and can be manufactured. These unique loci of points meet the requirements for stage efficiency and are arrived at by iteration between aerodynamic and mechanical loadings enabling the turbine and compressor to run in an efficient, safe, reliable and smooth manner. These points are unique and specific to the system. The locus that defines the airfoil profile includes a set of points with X, Y and Z coordinates relative to a reference origin coordinate system. The three-dimensional Cartesian coordinate system of X, Y and Z values given in scalable Table 1 below defines the profile of the inlet guide vane airfoil at various locations along its length. Scalable Table 1 lists data for a non-coated airfoil. The envelope/tolerance for the coordinates is about +/−5% of the chord length 350 in a direction normal to any airfoil surface location, or about +/−0.25 inches in a direction normal to any airfoil surface location. However, tolerances of about +/−0.15 inches to about +/−0.25 inches, or about +/−3% to about +/−5% in a direction normal to an airfoil surface location may also be used, as desired in the specific application.

The point data origin 230 may be the mid-point of the suction or pressure side of the base of the airfoil, the leading edge or trailing edge of the base of the airfoil, or any other suitable location as desired. The coordinate values for the X, Y and Z coordinates are set forth in non-dimensionalized units in scalable Table 1 although other units of dimensions may be used when the values are appropriately converted. As one example only, the Cartesian coordinate values of X, Y and Z may be convertible to dimensional distances by multiplying the X, Y and Z values by a multiplying by a constant number (e.g., 100). The number, used to convert the non-dimensional values to dimensional distances, may be a fraction (e.g., ½, ¼, etc.), decimal fraction (e.g., 0.5, 1.5, 10.25, etc.), integer (e.g., 1, 2, 10, 100, etc.) or a mixed number (e.g., 1½, 10½, etc.). The dimensional distances may be any suitable format (e.g., inches, feet, millimeters, centimeters, meters, etc.). As one non-limiting example only, the Cartesian coordinate system has orthogonally-related X, Y and Z axes and the X axis may lie generally parallel to the compressor rotor centerline, i.e., the rotary axis and a positive X coordinate value is axial toward the aft, i.e., exhaust end of the turbine. The positive Y coordinate value extends tangentially in the direction of rotation of the rotor and the positive Z coordinate value is radially outwardly toward the rotor blade tip or stator vane base. All the values in scalable Table 1 are given at room temperature and are unfilleted.

By defining X and Y coordinate values at selected locations in a Z direction (or height) normal to the X, Y plane, the profile section or airfoil shape of the airfoil, at each Z height along the length of the airfoil can be ascertained. By connecting the X and Y values with smooth continuing arcs, each profile section at each Z height is fixed. The airfoil profiles of the various surface locations between each Z height are determined by smoothly connecting the adjacent profile sections to one another to form the airfoil profile.

The Table 1 values are generated and shown from zero to four or more decimal places for determining the profile of the airfoil. As the airfoil heats up the associated stress and temperature will cause a change in the X, Y and Z values. Accordingly, the values for the profile given in Table 1 represent ambient, non-operating or non-hot conditions (e.g., room temperature) and are for an uncoated airfoil.

There are typical manufacturing tolerances as well as optional coatings which must be accounted for in the actual profile of the airfoil. Each section is joined smoothly with the other sections to form the complete airfoil shape. It will therefore be appreciated that +/−typical manufacturing tolerances, i.e., +/−values, including any coating thicknesses, are additive to the X and Y values given in Table 1 below. Accordingly, a distance of about +/−5% of chord length and/or +/−0.25 inches in a direction normal to a surface location along the airfoil profile defines an airfoil profile envelope for this particular airfoil design and compressor, i.e., a range of variation between measured points on the actual airfoil surface at nominal cold or room temperature and the ideal position of those points as given in the Table below at the same temperature. Additionally, a distance of about +/−5% of a chord length in a direction normal to an airfoil surface location along the airfoil profile also may define an airfoil profile envelope for this particular airfoil design. The data is scalable and the geometry pertains to all aerodynamic scales, at, above and/or below about 3,600 RPM. The inlet guide vane airfoil design is robust to this range of variation without impairment of mechanical and aerodynamic functions.

The coordinate values given in scalable TABLE 1 below provide the nominal profile for an exemplary stage compressor inlet guide vane.

TABLE 1 SUCTION SIDE PRESSURE SIDE X Y Z X Y Z 3.9560 −1.4429 −0.9575 −3.4503 0.4670 −0.9575 3.9610 −1.4318 −0.9575 −3.4500 0.4654 −0.9575 3.9650 −1.4161 −0.9575 −3.4492 0.4624 −0.9575 3.9652 −1.3960 −0.9575 −3.4474 0.4564 −0.9575 3.9587 −1.3727 −0.9575 −3.4422 0.4449 −0.9575 3.9388 −1.3472 −0.9575 −3.4310 0.4289 −0.9575 3.9028 −1.3253 −0.9575 −3.4045 0.4057 −0.9575 3.8571 −1.2988 −0.9575 −3.3629 0.3841 −0.9575 3.8017 −1.2664 −0.9575 −3.3034 0.3666 −0.9575 3.7358 −1.2279 −0.9575 −3.2272 0.3544 −0.9575 3.6589 −1.1823 −0.9575 −3.1274 0.3432 −0.9575 3.5683 −1.1281 −0.9575 −3.0119 0.3315 −0.9575 3.4640 −1.0651 −0.9575 −2.8887 0.3200 −0.9575 3.3459 −0.9936 −0.9575 −2.7500 0.3071 −0.9575 3.2139 −0.9136 −0.9575 −2.5961 0.2921 −0.9575 3.0680 −0.8255 −0.9575 −2.4268 0.2745 −0.9575 2.9077 −0.7294 −0.9575 −2.2501 0.2544 −0.9575 2.7401 −0.6299 −0.9575 −2.0658 0.2316 −0.9575 2.5647 −0.5276 −0.9575 −1.8742 0.2058 −0.9575 2.3813 −0.4228 −0.9575 −1.6753 0.1766 −0.9575 2.1897 −0.3163 −0.9575 −1.4690 0.1438 −0.9575 1.9897 −0.2084 −0.9575 −1.2556 0.1074 −0.9575 1.7812 −0.1001 −0.9575 −1.0350 0.0674 −0.9575 1.5640 0.0077 −0.9575 −0.8073 0.0235 −0.9575 1.3449 0.1110 −0.9575 −0.5801 −0.0230 −0.9575 1.1239 0.2093 −0.9575 −0.3535 −0.0722 −0.9575 0.9009 0.3026 −0.9575 −0.1273 −0.1240 −0.9575 0.6758 0.3905 −0.9575 0.0983 −0.1784 −0.9575 0.4485 0.4727 −0.9575 0.3233 −0.2349 −0.9575 0.2188 0.5490 −0.9575 0.5477 −0.2937 −0.9575 −0.0134 0.6189 −0.9575 0.7715 −0.3545 −0.9575 −0.2481 0.6823 −0.9575 0.9949 −0.4173 −0.9575 −0.4857 0.7386 −0.9575 1.2176 −0.4820 −0.9575 −0.7257 0.7872 −0.9575 1.4399 −0.5485 −0.9575 −0.9669 0.8272 −0.9575 1.6616 −0.6170 −0.9575 −1.2014 0.8569 −0.9575 1.8751 −0.6853 −0.9575 −1.4288 0.8769 −0.9575 2.0807 −0.7533 −0.9575 −1.6490 0.8876 −0.9575 2.2781 −0.8210 −0.9575 −1.8605 0.8897 −0.9575 2.4676 −0.8883 −0.9575 −2.0632 0.8839 −0.9575 2.6491 −0.9550 −0.9575 −2.2573 0.8708 −0.9575 2.8225 −1.0211 −0.9575 −2.4427 0.8513 −0.9575 2.9881 −1.0863 −0.9575 −2.6194 0.8253 −0.9575 3.1385 −1.1477 −0.9575 −2.7797 0.7953 −0.9575 3.2741 −1.2047 −0.9575 −2.9232 0.7624 −0.9575 3.3947 −1.2569 −0.9575 −3.0494 0.7271 −0.9575 3.5007 −1.3043 −0.9575 −3.1659 0.6884 −0.9575 3.5920 −1.3463 −0.9575 −3.2653 0.6500 −0.9575 3.6689 −1.3827 −0.9575 −3.3397 0.6157 −0.9575 3.7344 −1.4145 −0.9575 −3.3942 0.5795 −0.9575 3.7892 −1.4415 −0.9575 −3.4284 0.5440 −0.9575 3.8342 −1.4639 −0.9575 −3.4461 0.5116 −0.9575 3.8706 −1.4805 −0.9575 −3.4510 0.4917 −0.9575 3.9012 −1.4819 −0.9575 −3.4516 0.4785 −0.9575 3.9232 −1.4748 −0.9575 −3.4511 0.4719 −0.9575 3.9391 −1.4639 −0.9575 −3.4506 0.4686 −0.9575 3.9496 −1.4526 −0.9575 3.8833 −1.4385 0.0000 −3.3844 0.4323 0.0000 3.8880 −1.4276 0.0000 −3.3841 0.4307 0.0000 3.8916 −1.4120 0.0000 −3.3834 0.4278 0.0000 3.8914 −1.3923 0.0000 −3.3816 0.4219 0.0000 3.8842 −1.3695 0.0000 −3.3765 0.4108 0.0000 3.8641 −1.3451 0.0000 −3.3653 0.3952 0.0000 3.8286 −1.3240 0.0000 −3.3390 0.3730 0.0000 3.7837 −1.2983 0.0000 −3.2980 0.3526 0.0000 3.7292 −1.2671 0.0000 −3.2397 0.3363 0.0000 3.6644 −1.2297 0.0000 −3.1648 0.3251 0.0000 3.5888 −1.1857 0.0000 −3.0666 0.3145 0.0000 3.4996 −1.1334 0.0000 −2.9532 0.3035 0.0000 3.3971 −1.0725 0.0000 −2.8322 0.2925 0.0000 3.2809 −1.0033 0.0000 −2.6960 0.2801 0.0000 3.1510 −0.9260 0.0000 −2.5448 0.2656 0.0000 3.0075 −0.8407 0.0000 −2.3786 0.2483 0.0000 2.8500 −0.7476 0.0000 −2.2051 0.2287 0.0000 2.6852 −0.6513 0.0000 −2.0241 0.2063 0.0000 2.5129 −0.5522 0.0000 −1.8360 0.1807 0.0000 2.3328 −0.4506 0.0000 −1.6407 0.1520 0.0000 2.1449 −0.3473 0.0000 −1.4384 0.1196 0.0000 1.9490 −0.2428 0.0000 −1.2291 0.0837 0.0000 1.7447 −0.1379 0.0000 −1.0127 0.0442 0.0000 1.5318 −0.0332 0.0000 −0.7895 0.0010 0.0000 1.3170 0.0673 0.0000 −0.5669 −0.0448 0.0000 1.1005 0.1631 0.0000 −0.3448 −0.0933 0.0000 0.8819 0.2542 0.0000 −0.1234 −0.1444 0.0000 0.6613 0.3402 0.0000 0.0976 −0.1979 0.0000 0.4384 0.4211 0.0000 0.3181 −0.2535 0.0000 0.2133 0.4964 0.0000 0.5381 −0.3114 0.0000 −0.0143 0.5657 0.0000 0.7576 −0.3714 0.0000 −0.2445 0.6286 0.0000 0.9768 −0.4334 0.0000 −0.4776 0.6849 0.0000 1.1954 −0.4971 0.0000 −0.7124 0.7334 0.0000 1.4134 −0.5627 0.0000 −0.9485 0.7736 0.0000 1.6308 −0.6301 0.0000 −1.1780 0.8039 0.0000 1.8404 −0.6973 0.0000 −1.4009 0.8245 0.0000 2.0421 −0.7642 0.0000 −1.6164 0.8361 0.0000 2.2360 −0.8307 0.0000 −1.8234 0.8392 0.0000 2.4219 −0.8967 0.0000 −2.0218 0.8344 0.0000 2.6000 −0.9621 0.0000 −2.2119 0.8225 0.0000 2.7703 −1.0269 0.0000 −2.3936 0.8042 0.0000 2.9327 −1.0908 0.0000 −2.5670 0.7793 0.0000 3.0805 −1.1509 0.0000 −2.7241 0.7503 0.0000 3.2136 −1.2066 0.0000 −2.8651 0.7184 0.0000 3.3321 −1.2576 0.0000 −2.9889 0.6844 0.0000 3.4362 −1.3038 0.0000 −3.1033 0.6469 0.0000 3.5260 −1.3448 0.0000 −3.2008 0.6095 0.0000 3.6015 −1.3803 0.0000 −3.2738 0.5762 0.0000 3.6659 −1.4112 0.0000 −3.3275 0.5415 0.0000 3.7198 −1.4377 0.0000 −3.3617 0.5072 0.0000 3.7640 −1.4595 0.0000 −3.3797 0.4760 0.0000 3.8000 −1.4756 0.0000 −3.3850 0.4565 0.0000 3.8300 −1.4767 0.0000 −3.3857 0.4436 0.0000 3.8514 −1.4696 0.0000 −3.3852 0.4371 0.0000 3.8669 −1.4591 0.0000 −3.3848 0.4339 0.0000 3.8772 −1.4481 0.0000 3.8534 −1.4368 0.3906 −3.3578 0.4184 0.3906 3.8581 −1.4259 0.3906 −3.3575 0.4169 0.3906 3.8616 −1.4104 0.3906 −3.3567 0.4139 0.3906 3.8612 −1.3907 0.3906 −3.3549 0.4082 0.3906 3.8539 −1.3684 0.3906 −3.3498 0.3971 0.3906 3.8337 −1.3442 0.3906 −3.3387 0.3818 0.3906 3.7984 −1.3233 0.3906 −3.3125 0.3598 0.3906 3.7539 −1.2981 0.3906 −3.2718 0.3400 0.3906 3.6997 −1.2673 0.3906 −3.2138 0.3241 0.3906 3.6354 −1.2305 0.3906 −3.1395 0.3132 0.3906 3.5603 −1.1871 0.3906 −3.0421 0.3029 0.3906 3.4719 −1.1354 0.3906 −2.9297 0.2921 0.3906 3.3699 −1.0754 0.3906 −2.8096 0.2814 0.3906 3.2546 −1.0072 0.3906 −2.6746 0.2692 0.3906 3.1257 −0.9310 0.3906 −2.5246 0.2548 0.3906 2.9831 −0.8468 0.3906 −2.3598 0.2376 0.3906 2.8267 −0.7551 0.3906 −2.1877 0.2180 0.3906 2.6630 −0.6601 0.3906 −2.0083 0.1956 0.3906 2.4919 −0.5624 0.3906 −1.8218 0.1703 0.3906 2.3132 −0.4623 0.3906 −1.6281 0.1416 0.3906 2.1267 −0.3605 0.3906 −1.4275 0.1096 0.3906 1.9322 −0.2574 0.3906 −1.2200 0.0740 0.3906 1.7295 −0.1538 0.3906 −1.0055 0.0348 0.3906 1.5183 −0.0502 0.3906 −0.7841 −0.0081 0.3906 1.3053 0.0492 0.3906 −0.5633 −0.0536 0.3906 1.0904 0.1443 0.3906 −0.3430 −0.1016 0.3906 0.8735 0.2348 0.3906 −0.1233 −0.1524 0.3906 0.6547 0.3205 0.3906 0.0960 −0.2054 0.3906 0.4337 0.4009 0.3906 0.3147 −0.2607 0.3906 0.2104 0.4759 0.3906 0.5331 −0.3180 0.3906 −0.0155 0.5448 0.3906 0.7510 −0.3775 0.3906 −0.2442 0.6074 0.3906 0.9683 −0.4390 0.3906 −0.4752 0.6633 0.3906 1.1850 −0.5023 0.3906 −0.7078 0.7116 0.3906 1.4013 −0.5674 0.3906 −0.9417 0.7515 0.3906 1.6169 −0.6346 0.3906 −1.1692 0.7817 0.3906 1.8247 −0.7014 0.3906 −1.3903 0.8024 0.3906 2.0247 −0.7679 0.3906 −1.6035 0.8143 0.3906 2.2169 −0.8341 0.3906 −1.8084 0.8179 0.3906 2.4012 −0.8997 0.3906 −2.0050 0.8138 0.3906 2.5779 −0.9647 0.3906 −2.1934 0.8024 0.3906 2.7468 −1.0288 0.3906 −2.3736 0.7847 0.3906 2.9079 −1.0921 0.3906 −2.5455 0.7607 0.3906 3.0545 −1.1515 0.3906 −2.7014 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−0.1408 18.5893 −0.8087 0.1998 18.5893 0.4890 −0.1478 18.5893 −0.9396 0.2025 18.5893 0.6176 −0.1551 18.5893 −1.0660 0.2028 18.5893 0.7420 −0.1622 18.5893 −1.1881 0.2010 18.5893 0.8620 −0.1692 18.5893 −1.3058 0.1969 18.5893 0.9778 −0.1761 18.5893 −1.4190 0.1906 18.5893 1.0893 −0.1829 18.5893 −1.5278 0.1823 18.5893 1.1965 −0.1894 18.5893 −1.6319 0.1719 18.5893 1.2993 −0.1959 18.5893 −1.7315 0.1594 18.5893 1.3979 −0.2022 18.5893 −1.8264 0.1451 18.5893 1.4880 −0.2080 18.5893 −1.9124 0.1298 18.5893 1.5694 −0.2134 18.5893 −1.9893 0.1137 18.5893 1.6423 −0.2183 18.5893 −2.0571 0.0972 18.5893 1.7065 −0.2227 18.5893 −2.1202 0.0796 18.5893 1.7623 −0.2266 18.5893 −2.1741 0.0622 18.5893 1.8094 −0.2300 18.5893 −2.2150 0.0467 18.5893 1.8497 −0.2329 18.5893 −2.2466 0.0320 18.5893 1.8835 −0.2353 18.5893 −2.2680 0.0171 18.5893 1.9114 −0.2373 18.5893 −2.2809 0.0022 18.5893 1.9336 −0.2382 18.5893 −2.2856 −0.0076 18.5893 1.9499 −0.2330 18.5893 −2.2868 −0.0145 18.5893 1.9600 −0.2250 18.5893 −2.2868 −0.0180 18.5893 1.9662 −0.2163 18.5893 −2.2867 −0.0197 18.5893 1.9694 −0.2083 18.5893 1.9286 −0.1798 18.9937 −2.2552 −0.0248 18.9937 1.9289 −0.1734 18.9937 −2.2551 −0.0256 18.9937 1.9277 −0.1648 18.9937 −2.2547 −0.0273 18.9937 1.9238 −0.1548 18.9937 −2.2535 −0.0305 18.9937 1.9161 −0.1445 18.9937 −2.2502 −0.0364 18.9937 1.9016 −0.1353 18.9937 −2.2428 −0.0440 18.9937 1.8798 −0.1306 18.9937 −2.2263 −0.0536 18.9937 1.8525 −0.1255 18.9937 −2.2021 −0.0608 18.9937 1.8191 −0.1193 18.9937 −2.1686 −0.0652 18.9937 1.7795 −0.1121 18.9937 −2.1265 −0.0680 18.9937 1.7331 −0.1036 18.9937 −2.0717 −0.0703 18.9937 1.6783 −0.0936 18.9937 −2.0084 −0.0717 18.9937 1.6151 −0.0822 18.9937 −1.9408 −0.0728 18.9937 1.5433 −0.0695 18.9937 −1.8649 −0.0736 18.9937 1.4632 −0.0553 18.9937 −1.7805 −0.0743 18.9937 1.3746 −0.0399 18.9937 −1.6877 −0.0755 18.9937 1.2773 −0.0235 18.9937 −1.5905 −0.0768 18.9937 1.1759 −0.0067 18.9937 −1.4892 −0.0785 18.9937 1.0702 0.0103 18.9937 −1.3837 −0.0805 18.9937 0.9601 0.0274 18.9937 −1.2741 −0.0830 18.9937 0.8456 0.0446 18.9937 −1.1601 −0.0855 18.9937 0.7268 0.0616 18.9937 −1.0420 −0.0882 18.9937 0.6037 0.0784 18.9937 −0.9195 −0.0910 18.9937 0.4762 0.0949 18.9937 −0.7930 −0.0941 18.9937 0.3487 0.1105 18.9937 −0.6664 −0.0973 18.9937 0.2210 0.1252 18.9937 −0.5398 −0.1010 18.9937 0.0932 0.1388 18.9937 −0.4132 −0.1051 18.9937 −0.0347 0.1514 18.9937 −0.2867 −0.1096 18.9937 −0.1628 0.1629 18.9937 −0.1601 −0.1143 18.9937 −0.2909 0.1732 18.9937 −0.0336 −0.1193 18.9937 −0.4192 0.1821 18.9937 0.0928 −0.1247 18.9937 −0.5475 0.1895 18.9937 0.2194 −0.1303 18.9937 −0.6759 0.1954 18.9937 0.3459 −0.1361 18.9937 −0.8043 0.1994 18.9937 0.4724 −0.1420 18.9937 −0.9329 0.2013 18.9937 0.5989 −0.1480 18.9937 −1.0572 0.2010 18.9937 0.7211 −0.1539 18.9937 −1.1772 0.1985 18.9937 0.8392 −0.1597 18.9937 −1.2928 0.1938 18.9937 0.9530 −0.1654 18.9937 −1.4040 0.1871 18.9937 1.0626 −0.1709 18.9937 −1.5108 0.1784 18.9937 1.1680 −0.1764 18.9937 −1.6132 0.1677 18.9937 1.2691 −0.1817 18.9937 −1.7109 0.1548 18.9937 1.3661 −0.1869 18.9937 −1.8041 0.1404 18.9937 1.4546 −0.1917 18.9937 −1.8885 0.1250 18.9937 1.5347 −0.1961 18.9937 −1.9639 0.1088 18.9937 1.6063 −0.2001 18.9937 −2.0306 0.0923 18.9937 1.6696 −0.2038 18.9937 −2.0924 0.0748 18.9937 1.7243 −0.2071 18.9937 −2.1454 0.0573 18.9937 1.7707 −0.2098 18.9937 −2.1855 0.0420 18.9937 1.8103 −0.2122 18.9937 −2.2163 0.0272 18.9937 1.8436 −0.2143 18.9937 −2.2373 0.0123 18.9937 1.8710 −0.2160 18.9937 −2.2498 −0.0022 18.9937 1.8928 −0.2163 18.9937 −2.2543 −0.0120 18.9937 1.9087 −0.2107 18.9937 −2.2556 −0.0188 18.9937 1.9184 −0.2027 18.9937 −2.2556 −0.0222 18.9937 1.9243 −0.1939 18.9937 −2.2554 −0.0239 18.9937 1.9274 −0.1861 18.9937 1.9016 −0.1662 19.2633 −2.2343 −0.0275 19.2633 1.9019 −0.1597 19.2633 −2.2341 −0.0283 19.2633 1.9008 −0.1513 19.2633 −2.2336 −0.0299 19.2633 1.8969 −0.1414 19.2633 −2.2326 −0.0332 19.2633 1.8892 −0.1311 19.2633 −2.2292 −0.0390 19.2633 1.8750 −0.1220 19.2633 −2.2219 −0.0466 19.2633 1.8536 −0.1172 19.2633 −2.2057 −0.0562 19.2633 1.8264 −0.1122 19.2633 −2.1819 −0.0634 19.2633 1.7935 −0.1063 19.2633 −2.1488 −0.0680 19.2633 1.7544 −0.0993 19.2633 −2.1072 −0.0710 19.2633 1.7084 −0.0911 19.2633 −2.0530 −0.0733 19.2633 1.6542 −0.0815 19.2633 −1.9904 −0.0750 19.2633 1.5917 −0.0705 19.2633 −1.9238 −0.0762 19.2633 1.5207 −0.0581 19.2633 −1.8486 −0.0771 19.2633 1.4414 −0.0443 19.2633 −1.7652 −0.0780 19.2633 1.3537 −0.0295 19.2633 −1.6735 −0.0792 19.2633 1.2576 −0.0135 19.2633 −1.5775 −0.0805 19.2633 1.1573 0.0027 19.2633 −1.4774 −0.0821 19.2633 1.0526 0.0191 19.2633 −1.3731 −0.0841 19.2633 0.9437 0.0356 19.2633 −1.2647 −0.0864 19.2633 0.8306 0.0520 19.2633 −1.1520 −0.0888 19.2633 0.7131 0.0685 19.2633 −1.0352 −0.0913 19.2633 0.5913 0.0846 19.2633 −0.9142 −0.0938 19.2633 0.4653 0.1005 19.2633 −0.7891 −0.0966 19.2633 0.3391 0.1154 19.2633 −0.6640 −0.0995 19.2633 0.2129 0.1294 19.2633 −0.5390 −0.1027 19.2633 0.0865 0.1424 19.2633 −0.4139 −0.1062 19.2633 −0.0400 0.1545 19.2633 −0.2888 −0.1102 19.2633 −0.1666 0.1655 19.2633 −0.1637 −0.1143 19.2633 −0.2933 0.1752 19.2633 −0.0386 −0.1188 19.2633 −0.4201 0.1835 19.2633 0.0865 −0.1235 19.2633 −0.5469 0.1903 19.2633 0.2116 −0.1283 19.2633 −0.6739 0.1957 19.2633 0.3366 −0.1334 19.2633 −0.8009 0.1992 19.2633 0.4617 −0.1386 19.2633 −0.9280 0.2007 19.2633 0.5867 −0.1438 19.2633 −1.0508 0.1999 19.2633 0.7075 −0.1489 19.2633 −1.1695 0.1970 19.2633 0.8242 −0.1540 19.2633 −1.2837 0.1920 19.2633 0.9367 −0.1589 19.2633 −1.3937 0.1850 19.2633 1.0451 −0.1637 19.2633 −1.4992 0.1759 19.2633 1.1493 −0.1684 19.2633 −1.6003 0.1650 19.2633 1.2493 −0.1730 19.2633 −1.6969 0.1521 19.2633 1.3452 −0.1775 19.2633 −1.7890 0.1374 19.2633 1.4327 −0.1816 19.2633 −1.8724 0.1220 19.2633 1.5119 −0.1854 19.2633 −1.9469 0.1058 19.2633 1.5827 −0.1889 19.2633 −2.0127 0.0892 19.2633 1.6452 −0.1921 19.2633 −2.0738 0.0717 19.2633 1.6994 −0.1948 19.2633 −2.1261 0.0542 19.2633 1.7452 −0.1973 19.2633 −2.1656 0.0389 19.2633 1.7843 −0.1993 19.2633 −2.1961 0.0242 19.2633 1.8173 −0.2011 19.2633 −2.2167 0.0093 19.2633 1.8443 −0.2027 19.2633 −2.2290 −0.0051 19.2633 1.8659 −0.2029 19.2633 −2.2334 −0.0148 19.2633 1.8817 −0.1973 19.2633 −2.2345 −0.0216 19.2633 1.8914 −0.1891 19.2633 −2.2345 −0.0249 19.2633 1.8973 −0.1803 19.2633 −2.2343 −0.0266 19.2633 1.9004 −0.1725 19.2633 1.8753 −0.1530 19.5329 −2.2131 −0.0301 19.5329 1.8755 −0.1467 19.5329 −2.2130 −0.0309 19.5329 1.8743 −0.1383 19.5329 −2.2126 −0.0325 19.5329 1.8706 −0.1285 19.5329 −2.2115 −0.0357 19.5329 1.8631 −0.1184 19.5329 −2.2082 −0.0415 19.5329 1.8492 −0.1092 19.5329 −2.2011 −0.0491 19.5329 1.8279 −0.1044 19.5329 −2.1851 −0.0586 19.5329 1.8011 −0.0997 19.5329 −2.1616 −0.0660 19.5329 1.7685 −0.0939 19.5329 −2.1289 −0.0706 19.5329 1.7297 −0.0871 19.5329 −2.0878 −0.0738 19.5329 1.6843 −0.0791 19.5329 −2.0342 −0.0764 19.5329 1.6307 −0.0698 19.5329 −1.9724 −0.0782 19.5329 1.5689 −0.0591 19.5329 −1.9064 −0.0795 19.5329 1.4987 −0.0471 19.5329 −1.8322 −0.0806 19.5329 1.4202 −0.0338 19.5329 −1.7497 −0.0816 19.5329 1.3335 −0.0194 19.5329 −1.6589 −0.0829 19.5329 1.2384 −0.0040 19.5329 −1.5641 −0.0842 19.5329 1.1392 0.0117 19.5329 −1.4652 −0.0858 19.5329 1.0358 0.0275 19.5329 −1.3620 −0.0877 19.5329 0.9280 0.0434 19.5329 −1.2548 −0.0899 19.5329 0.8161 0.0593 19.5329 −1.1434 −0.0921 19.5329 0.6999 0.0750 19.5329 −1.0279 −0.0944 19.5329 0.5795 0.0906 19.5329 −0.9084 −0.0967 19.5329 0.4548 0.1058 19.5329 −0.7847 −0.0991 19.5329 0.3300 0.1201 19.5329 −0.6609 −0.1016 19.5329 0.2052 0.1335 19.5329 −0.5372 −0.1044 19.5329 0.0803 0.1459 19.5329 −0.4135 −0.1076 19.5329 −0.0448 0.1575 19.5329 −0.2898 −0.1110 19.5329 −0.1700 0.1679 19.5329 −0.1662 −0.1146 19.5329 −0.2953 0.1770 19.5329 −0.0424 −0.1184 19.5329 −0.4207 0.1848 19.5329 0.0812 −0.1224 19.5329 −0.5461 0.1912 19.5329 0.2049 −0.1266 19.5329 −0.6716 0.1960 19.5329 0.3286 −0.1309 19.5329 −0.7971 0.1991 19.5329 0.4522 −0.1354 19.5329 −0.9228 0.2001 19.5329 0.5759 −0.1400 19.5329 −1.0443 0.1988 19.5329 0.6954 −0.1444 19.5329 −1.1615 0.1955 19.5329 0.8108 −0.1487 19.5329 −1.2744 0.1902 19.5329 0.9221 −0.1529 19.5329 −1.3831 0.1828 19.5329 1.0293 −0.1570 19.5329 −1.4873 0.1735 19.5329 1.1324 −0.1610 19.5329 −1.5873 0.1625 19.5329 1.2312 −0.1648 19.5329 −1.6827 0.1494 19.5329 1.3260 −0.1686 19.5329 −1.7738 0.1346 19.5329 1.4126 −0.1721 19.5329 −1.8561 0.1192 19.5329 1.4909 −0.1753 19.5329 −1.9297 0.1028 19.5329 1.5610 −0.1782 19.5329 −1.9947 0.0863 19.5329 1.6228 −0.1809 19.5329 −2.0551 0.0687 19.5329 1.6763 −0.1833 19.5329 −2.1066 0.0512 19.5329 1.7216 −0.1854 19.5329 −2.1456 0.0359 19.5329 1.7604 −0.1871 19.5329 −2.1757 0.0212 19.5329 1.7929 −0.1886 19.5329 −2.1961 0.0065 19.5329 1.8197 −0.1900 19.5329 −2.2081 −0.0080 19.5329 1.8411 −0.1898 19.5329 −2.2123 −0.0175 19.5329 1.8564 −0.1837 19.5329 −2.2135 −0.0242 19.5329 1.8656 −0.1755 19.5329 −2.2135 −0.0276 19.5329 1.8713 −0.1669 19.5329 −2.2133 −0.0292 19.5329 1.8741 −0.1592 19.5329 1.7719 −0.1023 20.6113 −2.1288 −0.0403 20.6113 1.7721 −0.0963 20.6113 −2.1286 −0.0411 20.6113 1.7709 −0.0883 20.6113 −2.1282 −0.0426 20.6113 1.7674 −0.0789 20.6113 −2.1272 −0.0457 20.6113 1.7605 −0.0691 20.6113 −2.1242 −0.0512 20.6113 1.7475 −0.0599 20.6113 −2.1175 −0.0586 20.6113 1.7274 −0.0550 20.6113 −2.1026 −0.0682 20.6113 1.7018 −0.0509 20.6113 −2.0802 −0.0759 20.6113 1.6706 −0.0458 20.6113 −2.0493 −0.0812 20.6113 1.6335 −0.0399 20.6113 −2.0100 −0.0848 20.6113 1.5901 −0.0330 20.6113 −1.9590 −0.0882 20.6113 1.5388 −0.0248 20.6113 −1.8999 −0.0907 20.6113 1.4796 −0.0155 20.6113 −1.8370 −0.0927 20.6113 1.4125 −0.0050 20.6113 −1.7661 −0.0944 20.6113 1.3374 0.0067 20.6113 −1.6874 −0.0957 20.6113 1.2545 0.0192 20.6113 −1.6008 −0.0973 20.6113 1.1636 0.0326 20.6113 −1.5102 −0.0989 20.6113 1.0687 0.0463 20.6113 −1.4157 −0.1005 20.6113 0.9698 0.0599 20.6113 −1.3173 −0.1022 20.6113 0.8669 0.0737 20.6113 −1.2150 −0.1040 20.6113 0.7599 0.0874 20.6113 −1.1086 −0.1057 20.6113 0.6488 0.1007 20.6113 −0.9984 −0.1072 20.6113 0.5336 0.1138 20.6113 −0.8841 −0.1086 20.6113 0.4145 0.1264 20.6113 −0.7661 −0.1098 20.6113 0.2952 0.1383 20.6113 −0.6479 −0.1110 20.6113 0.1759 0.1494 20.6113 −0.5298 −0.1121 20.6113 0.0564 0.1596 20.6113 −0.4117 −0.1133 20.6113 −0.0630 0.1690 20.6113 −0.2935 −0.1148 20.6113 −0.1825 0.1772 20.6113 −0.1754 −0.1162 20.6113 −0.3022 0.1842 20.6113 −0.0572 −0.1176 20.6113 −0.4219 0.1899 20.6113 0.0608 −0.1191 20.6113 −0.5417 0.1943 20.6113 0.1789 −0.1207 20.6113 −0.6615 0.1973 20.6113 0.2971 −0.1224 20.6113 −0.7814 0.1983 20.6113 0.4152 −0.1241 20.6113 −0.9013 0.1974 20.6113 0.5334 −0.1258 20.6113 −1.0171 0.1946 20.6113 0.6475 −0.1273 20.6113 −1.1289 0.1898 20.6113 0.7578 −0.1288 20.6113 −1.2366 0.1832 20.6113 0.8641 −0.1300 20.6113 −1.3402 0.1747 20.6113 0.9665 −0.1312 20.6113 −1.4396 0.1645 20.6113 1.0649 −0.1324 20.6113 −1.5348 0.1525 20.6113 1.1594 −0.1335 20.6113 −1.6257 0.1388 20.6113 1.2500 −0.1344 20.6113 −1.7123 0.1235 20.6113 1.3327 −0.1354 20.6113 −1.7907 0.1077 20.6113 1.4075 −0.1363 20.6113 −1.8608 0.0911 20.6113 1.4744 −0.1371 20.6113 −1.9226 0.0745 20.6113 1.5335 −0.1380 20.6113 −1.9799 0.0569 20.6113 1.5847 −0.1388 20.6113 −2.0289 0.0395 20.6113 1.6280 −0.1395 20.6113 −2.0658 0.0242 20.6113 1.6650 −0.1401 20.6113 −2.0942 0.0096 20.6113 1.6961 −0.1406 20.6113 −2.1132 −0.0049 20.6113 1.7216 −0.1411 20.6113 −2.1243 −0.0191 20.6113 1.7419 −0.1394 20.6113 −2.1282 −0.0283 20.6113 1.7556 −0.1323 20.6113 −2.1291 −0.0346 20.6113 1.7637 −0.1239 20.6113 −2.1291 −0.0379 20.6113 1.7686 −0.1155 20.6113 −2.1289 −0.0395 20.6113 1.7710 −0.1081 20.6113

It will also be appreciated that the airfoil 200 disclosed in the above scalable Table 1 may be non-scaled, scaled up or scaled down geometrically for use in other similar turbine/compressor designs. Consequently, the coordinate values set forth in Table 1 may be non-scaled, scaled upwardly or scaled downwardly such that the general airfoil profile shape remains unchanged. A scaled version of the coordinates in Table 1 would be represented by X, Y and Z coordinate values of Table 1, with the X, Y and Z non-dimensional coordinate values converted to inches or mm (or any suitable dimensional system), multiplied or divided by a constant number. The constant number may be a fraction, decimal fraction, integer or mixed number.

The article of manufacture may also have a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number. The X and Y coordinates, when connected by smooth continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height are joined smoothly with one another to form a complete suction-side airfoil shape. The X, Y and Z coordinate values being scalable as a function of a number to provide a non-scaled, scaled-up or scaled-down airfoil profile.

The article of manufacture may also have a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number. X and Y are coordinates which, when connected by smooth continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height are joined smoothly with one another to form a complete pressure-side airfoil shape. The X, Y and Z values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up and scaled-down airfoil.

The article of manufacture may be an airfoil or an inlet guide vane configured for use with a compressor. The suction-side airfoil shape may lie in an envelope within +/−5% of a chord length in a direction normal to a suction-side airfoil surface location, or +/−0.25 inches in a direction normal to a suction-side airfoil surface location.

The number, used to convert the non-dimensional values to dimensional distances, may be a fraction, decimal fraction, integer or mixed number. The height of the article of manufacture may be about 1 inch to about 50 inches, or any suitable height as desired in the specific application.

A compressor 2, according to an aspect of the present invention, may include a plurality of inlet guide vanes 21. Each of the inlet guide vanes 21 include an airfoil 200 having a suction-side 310 airfoil shape, the airfoil 200 having a nominal profile substantially in accordance with suction-side 310 Cartesian coordinate values of X, Y and Z set forth in scalable Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number. The number, used to convert the non-dimensional values to dimensional distances, may be a fraction, decimal fraction, integer or mixed number. X and Y are coordinates which, when connected by smooth continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined smoothly with one another to form a complete suction-side 310 airfoil shape.

The compressor 2, according to an aspect of the present invention, may also have a plurality of inlet guide vanes 21 having a pressure-side 320 nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number. The number (which would be the same number used for the suction side) may be a fraction, decimal fraction, integer or mixed number. X and Y are coordinates which, when connected by smooth continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined smoothly with one another to form a complete pressure-side airfoil shape.

An important term in this disclosure is profile. The profile is the range of the variation between measured points on an airfoil surface and the ideal position listed in scalable Table 1. The actual profile on a manufactured blade may be different than those in scalable Table 1 and the design is robust to this variation meaning that mechanical and aerodynamic function are not impaired. As noted above, an approximately + or −5% chord and/or 0.25 inch profile tolerance is used herein. The X, Y and Z values are all non-dimensionalized.

The following are non-limiting examples of the airfoil profiles embodied by the present invention. On some compressors, each airfoil profile section (e.g., at each Z height) may be connected by substantially smooth continuing arcs. On other compressors, some of the airfoil profile sections may be connected by substantially smooth continuing arcs. Embodiments of the present invention may also be employed by a compressor having stage(s) with no airfoil profile sections connected by substantially smooth continuing arcs.

The disclosed airfoil shape increases reliability and is specific to the machine conditions and specifications. The airfoil shape provides a unique profile to achieve (1) interaction between other stages in the compressor; (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical blade or vane loadings. The disclosed loci of points allow the gas turbine and compressor or any other suitable turbine/compressor to run in an efficient, safe and smooth manner. As also noted, any scale of the disclosed airfoil may be adopted as long as (1) interaction between other stages in the compressor, (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical blade loadings are maintained in the scaled compressor.

The airfoil 200 described herein thus improves overall compressor 2 efficiency. Specifically, the airfoil 200 provides the desired turbine/compressor efficiency lapse rate (ISO, hot, cold, part load, etc.). The airfoil 200 also meets all aeromechanics, loading and stress requirements.

It should be understood that the finished article of manufacture, blade or vane does not necessarily include all the sections defined in the one or more tables listed above. The portion of the airfoil proximal to a platform (or dovetail) and/or tip may not be defined by an airfoil profile section. It should be considered that the airfoil proximal to the platform or tip may vary due to several imposed constraints. The airfoil contains a main profile section that is substantially defined between the inner and outer flowpath walls. The remaining sections of the airfoil may be partly, at least partly or completely located outside of the flowpath. At least some of these remaining sections may be employed to improve the curve fitting of the airfoil at its radially inner or outer portions. The skilled reader will appreciate that a suitable fillet radius may be applied between the platform and the airfoil portion of the article of manufacture, blade or vane.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims. 

1. An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
 2. The article of manufacture according to claim 1, wherein the article of manufacture comprises an airfoil.
 3. The article of manufacture according to claim 1, wherein the article of manufacture comprises an inlet guide vane configured for use with a compressor.
 4. The article of manufacture according to claim 1, wherein the airfoil shape lies in an envelope within at least one of: +/−5% of a chord length in a direction normal to an airfoil surface location; and +/−0.25 inches in a direction normal to an airfoil surface location.
 5. The article of manufacture according to claim 1, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, decimal fraction, integer and mixed number.
 6. The article of manufacture according to claim 1, wherein a height of the article of manufacture is about 1 inch to about 50 inches.
 7. An article of manufacture having a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, the X, Y and Z coordinate values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up and scaled-down airfoil profile.
 8. The article of manufacture according to claim 7, wherein the article of manufacture comprises an airfoil.
 9. The article of manufacture according to claim 7, wherein the article of manufacture comprises an inlet guide vane configured for use with a compressor.
 10. The article of manufacture according to claim 7, wherein the suction-side airfoil shape lies in an envelope within at least one of: +/−5% of a chord length in a direction normal to a suction-side airfoil surface location; and +/−0.25 inches in a direction normal to a suction-side airfoil surface location.
 11. The article of manufacture according to claim 7, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, decimal fraction, integer and mixed number.
 12. The article of manufacture according to claim 7, wherein a height of the article of manufacture is about 1 inch to about 50 inches.
 13. The article of manufacture according to claim 7, further comprising the article of manufacture having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape, the X, Y and Z values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up and scaled-down airfoil.
 14. A compressor comprising a plurality of inlet guide vanes, each of the inlet guide vanes including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape.
 15. The compressor according to claim 14, wherein the suction-side airfoil shape lies in an envelope within at least one of: +/−5% of a chord length in a direction normal to a suction-side airfoil surface location; and +/−0.25 inches in a direction normal to a suction-side airfoil surface location.
 16. The compressor according to claim 14, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, decimal fraction, integer and mixed number.
 17. The compressor according to claim 14, wherein a height of each inlet guide vane is about 1 inch to about 50 inches.
 18. The compressor according to claim 14, further comprising each of the plurality of inlet guide vanes having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by the number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape.
 19. The compressor according to claim 18, wherein the pressure-side airfoil shape lies in an envelope within at least one of: +/−5% of a chord length in a direction normal to a pressure-side airfoil surface location; and +/−0.25 inches in a direction normal to a pressure-side airfoil surface location.
 20. The compressor according to claim 18, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, decimal fraction, integer and mixed number. 